Avionica UD1&2

Question

Which of the following loads of the gear is the biggest one

Answer 1

Vertical load

Answer 2

Gear recoil

Answer 3

Aerodynamic loads

Answer 4

a) High pressure system with a heat exchanger with ambient air

Answer 5

b) High and low pressure system with a heat exchanger between them

Answer 6

c) High and medium pressure system with an anti-return valve

Answer 7

d) Answer c and also with a heat exchanger with the fan flow

Answer 8

Leading edge

Answer 9

Trailing edge

Answer 10

c/2 of the chord

Answer 11

With more temperature less fatigue

Answer 12

Traction is the load that causes more fatigue

Answer 13

Corrosion decreases fatigue

Answer 14

Welding decreases fatigue

Answer 15

There are three types: cyclical, wets, and evaporative.

Answer 16

In aviation there are only anti-icing systems, not de-icing.

Answer 17

There are mainly three types: cyclic, by evaporation and wets. The latter are in danger of ice forming downstream.

Answer 18

All of the above are false.

Answer 19

a) Movement of the control surfaces (flaps, slats…)

Answer 20

b) Cabin pressurization and air conditioning

Answer 21

c) Pitot tube anti-icing

Answer 22

d) As a help to the afterburner

Answer 23

Non of them

Answer 24

It is based on a fluid heating system.

Answer 25

It consists of an electrical resistance system inside the pitot tube.

Answer 26

It is based on an electrical heating system of the outer surface of the pitot tube.

Answer 27

It is false that there is an anti-ice system in the pitot complex since the formation of ice in it is not contemplated.

Answer 28

a) It should exist a shut-off valve in case of emergency

Answer 29

b) The bleed quantity should be the minimum

Answer 30

c) It should be situated far from engine

Answer 31

d) A system should be integrated to report the status of the valves

Answer 32

Fail safe structure

Answer 33

Life safe structure

Answer 34

Jar 23 structure

Answer 35

Primary structure

Answer 36

The system is based on an electromagnetic wave that induces a current on the edge surface.

Answer 37

It is effective against very thin ice, even 0.7mm.

Answer 38

The system has a high consumption.

Answer 39

a) and b) are correct, c) is incorrect.

Answer 40

a) Puffers

Answer 41

c) Directional nozzle

Answer 42

d) This system doesn’t exist

Answer 43

Mechanical

Answer 44

The El-Thermal and Bleed Air systems are capable of removing thinner ice than the Pneumatic Boots and Expulsive systems, and they also have shorter life cycles.

Answer 45

El-Thermal and Bleed Air systems have infinite life cycles, but Pneumatic Boots and Expulsive systems can remove thinner ice.

Answer 46

El-Thermal and Bleed Air systems have infinite life cycles and also remove thinner ice than Pneumatic Boots and Expulsive systems.

Answer 47

All four systems have infinite life cycles but the El-Thermal and Bleed Air systems can remove thinner ice.

Answer 48

a) They can replace to the hydraulic system in any case

Answer 49

b) Usually they have more applications than the hydraulic system

Answer 50

c) They require high working pressures

Answer 51

d) All of above are false

Answer 52

The first point where icing occurs is generally in the ice detection system, due to its characteristics such as fine edges and the stagnation point condition.

Answer 53

The first point where ice formation takes place is at the wing ends.

Answer 54

A preventive measure when flying in icy conditions is the use of the autopilot.

Answer 55

The “Vibrating rod ice detector” is the most effective and extended flight ice detection system.

Answer 56

The statements a) and d) are correct.

Answer 57

a) It need low pressures for work

Answer 58

b) It don’t need a return route, the air is available at the atmosphere

Answer 59

c) It’s rare to have leaks

Answer 60

d) All of above are advantages

Answer 61

Fatigue reduction

Answer 62

Properties

Answer 63

Maintenance

Answer 64

The propeller De-Icing system involves a reduction in aerodynamic capacities as well as mass unbalanced that can cause vibrations.

Answer 65

The engine's antifreeze system normally mixes hot air with oil.

Answer 66

Statements a) and b) are correct.

Answer 67

All the statements are false.

Answer 68

a) Engine compressor in jet engines

Answer 69

b) Turbocharges in no jet engines

Answer 70

c) Engine turbine in jet engines

Answer 71

d) a and b are true

Answer 72

A key solution against damage from electric shock (lightning) on aircraft is to make the structure as a whole a good electrical conductor.

Answer 73

Approximately an aircraft suffers 1 lightning strike per 1500 flight hours.

Answer 74

Continuity in the structure of the aircraft in addition to ensuring that it acts as a "mesh" have no importance in terms of lightning strikes.

Answer 75

Normally tests and simulations are carried out to determine the areas most susceptible to damage.

Answer 76

a) Must go through a conditioning system before being used

Answer 77

b) Can be used directly from the engine

Answer 78

c) Usually it is only use during the aircraft is on ground

Answer 79

d) All of above are false

Answer 80

Smooth contours to minimize drag

Answer 81

Cylindrical shape to minimize drag

Answer 82

Area rule to minimize drag

Answer 83

Wingspan rule to maximize lift

Answer 84

The phenomenon takes place because the structure is positively charged.

Answer 85

The phenomenon occurs due to the negative charge of the structure, and is based on the electrical asymmetry that takes place between the different parts of the aircraft.

Answer 86

The discharges can cause electronic noise in the systems, and even greater damages if these are of great intensity.

Answer 87

b) and c) are correct.

Answer 88

Cylindrical

Answer 89

Triangular

Answer 90

False, the Kreuger flap does not change the curvature of the aerodynamic profile

Answer 91

False, with the Slat the same thing happens

Answer 92

Airlines aircrafts

Answer 93

Military aircrafts

Answer 94

Light gliders

Answer 95

Articulated Rods

Answer 96

None of them

Answer 97

Easyly to repair

Answer 98

Reduced weight

Answer 99

More tolerant to damage

Answer 100

All of the above

Answer 101

It provides a faster actuation

Answer 102

It provides a greater force

Answer 103

Less weight

Answer 104

All of the above, which is called torsion box

Answer 105

Unreliable system due to actuator

Answer 106

The system crashed when receiving conflicting commands between pilot and actuator

Answer 107

Delay between command and action on control surfaces

Answer 108

Very heavy wiring and electrical system

Answer 109

30 seconds

Answer 110

90 seconds

Answer 111

Two minutes

Answer 112

Three minutes

Answer 113

Single phase (monophasic)

Answer 114

Two phase (bifasic)

Answer 115

Three phase

Answer 116

None of them

Answer 117

Structural elements

Answer 118

Engine elements

Answer 119

Electric elements

Answer 120

Fire protection elements

Answer 121

False, the IAP does not have an actuator

Answer 122

False, the PBW does not have an electric motor.

Answer 123

High-speed aircrafts

Answer 124

Low-speed aircrafts

Answer 125

Supersonic aircrafts

Answer 126

Acrobatic aircrafts

Answer 127

False, it was first tested on 2017

Answer 128

True, and it is never going to be tested due to its complexity

Answer 129

False, it was first tested on 2019

Answer 130

Double lift

Answer 131

Easiest production

Answer 132

Esthetical reasons

Answer 133

Structural strengths

Answer 134

a. Any part of the wing span

Answer 135

b. The main spar

Answer 136

c. The main span or any stringer, it doesn´t matter

Answer 137

d. There are no wing mounted landing gears

Answer 138

a. Any part of the wing span

Answer 139

b. The main spar

Answer 140

c. The main span or any stringer, it doesn´t matter

Answer 141

d. There are no wing mounted landing gears

Answer 142

Compression efforts

Answer 143

Tension efforts

Answer 144

Both compression and torsion.

Answer 145

The main advantage was drag reduction

Answer 146

a. The joint of two spars from the wing to the main longeron of the fuselaje

Answer 147

b. The addition of auxiliar spars

Answer 148

c. Both A and B are correct

Answer 149

d. None of the previous is correct

Answer 150

a. The joint of two spars from the wing to the main longeron of the fuselaje

Answer 151

b. The addition of auxiliar spars

Answer 152

c. Both A and B are correct

Answer 153

d. None of the previous is correct

Answer 154

Compression

Answer 155

a. Shorter landing gear with lower weight

Answer 156

b. Fuselage closer to ground

Answer 157

c. Prevent floating (ground effect) when landing

Answer 158

d. Both B and C are correct

Answer 159

a. Shorter landing gear with lower weight

Answer 160

b. Fuselage closer to ground

Answer 161

c. Prevent floating (ground effect) when landing

Answer 162

d. Both B and C are correct

Answer 163

Strain or stress indifferently

Answer 164

a. Shorter landing gear with lower weight

Answer 165

b. Fuselage closer to ground

Answer 166

c. Prevent floating (ground effect) when landing

Answer 167

d. Both B and C are correct

Answer 168

a. Shorter landing gear with lower weight

Answer 169

b. Fuselage closer to ground

Answer 170

c. Prevent floating (ground effect) when landing

Answer 171

d. Both B and C are correct

Answer 172

Compression

Answer 173

a. Blocks pilot´s visibility in small aircrafts

Answer 174

b. Bigger engines are allowed

Answer 175

c. Requires structures to accomodate the landing gear

Answer 176

d. Both A and C are correct

Answer 177

a. Blocks pilot´s visibility in small aircrafts

Answer 178

b. Bigger engines are allowed

Answer 179

c. Requires structures to accomodate the landing gear

Answer 180

d. Both A and C are correct

Answer 181

Thinner coating

Answer 182

Thicker coating

Answer 183

More distance between anchor points

Answer 184

It is specific and fix for each material

Answer 185

c. Formeron

Answer 186

c. Formeron

Answer 187

Do not touch aerodynamic controls

Answer 188

Climb or descent immediately

Answer 189

Increase or reduce speed

Answer 190

Turn 90 degrees left or right

Answer 191

a. The tailplane has more ribs and les stringers to provide it more torsion rigidity

Answer 192

b. Both structures are exactly equal

Answer 193

c. In fighters the tailplane has formerons to give the fuselaje more rigidity

Answer 194

d. All the previous are false

Answer 195

a. The tailplane has more ribs and les stringers to provide it more torsion rigidity

Answer 196

b. Both structures are exactly equal

Answer 197

c. In fighters the tailplane has formerons to give the fuselaje more rigidity

Answer 198

d. All the previous are false

Answer 199

Protect passengers and payload

Answer 200

Resist applied loads

Answer 201

Provides thrust to the aircraft

Answer 202

Defines aerodynamic shape

Answer 203

a. Conventional

Answer 204

c. Twin tail

Answer 205

a. Conventional

Answer 206

c. Twin tail

Answer 207

Quadricycle

Answer 208

Multi-bogey.

Answer 209

a. Self-Lubricant System

Answer 210

b. Easy instalation

Answer 211

c. Low cost

Answer 212

d. Useful for small forces

Answer 213

Llantas “well base”, similares a las utilizadas en automoción.

Answer 214

Llantas “detachable flange”.

Answer 215

Llantas del tipo “Split hub”, que se se dividen en dos partes para facilitar el montaje y desmontaje de los neumáticos.

Answer 216

Ninguna de las anteriores.

Answer 217

a. The power of pums can work up to pressure ratio of 650, but the power of the pneumatic system is limited.

Answer 218

b. Pneumatic systems have stop time while hyudralic systems work continuously.

Answer 219

c. Hyudralic system has greater pressure losses due to viscous effects, and pneumatic dissipate more heat due to compressibility effects (hyudralics are generally more efficient)

Answer 220

d. Hyudralic system has greater pressure losses due to compressibility effects, and pneumatic dissipate more heat due to viscous effects (hyudralics are generally more efficient)

Answer 221

Common tyres as used in automotive.

Answer 222

Radial tyres, which are more resistant.

Answer 223

Both, regarding it is front tyre or principal gear

Answer 224

None of the above

Answer 225

a. Low viscosity

Answer 226

b. High viscosity

Answer 227

c. Resistance to heat

Answer 228

d. Good lubricant properties

Answer 229

Longitudinal, In order to improve the surface resistance during the braking

Answer 230

Both directions as in automotive

Answer 231

any of them because it is just aesthetic

Answer 232

None is the above

Answer 233

a. Vegetable-based, mineral-based, sintethic base

Answer 234

b. Vegetable-based, water-based, sintethic base

Answer 235

c. Vegetable-based, oil-based, sintetic base

Answer 236

d. Vegetable-based, fuel-based, hyudaulic base

Answer 237

It rains to much and the aeroplane surface gets wet

Answer 238

When the amount of water accumulated in front of the tyre is enough to lift it and make it lose its adhesion

Answer 239

Every time the runway is wet

Answer 240

None of the above

Answer 241

a. Reservoir

Answer 242

c. Selector Valve

Answer 243

d. Triple Acting clylinder

Answer 244

Primarias: alerones, estabilizadores horizontal y vertical. Primary: ailerons, horizontal and vertical stabilisers

Answer 245

Secondary: flaps and aero brakes .

Answer 246

A and B are correct

Answer 247

A y B are false

Answer 248

a. 3000-4000 psi

Answer 249

b. 200-100 psi

Answer 250

c. 15000-25000 psi

Answer 251

d. 1000-10000 psi

Answer 252

By Fly-by-wire technology

Answer 253

with cables and pulleys

Answer 254

by power-by-wire technology

Answer 255

None of above

Answer 256

a. Convert fluid pressure into linear motion

Answer 257

b. Convert linear motieon into circular motion

Answer 258

c. Convert fluid motion into linear pressure

Answer 259

d. All are false

Answer 260

Flaperones.

Answer 261

Ninguna de las anteriores.

Answer 262

a. Rotary selectors

Answer 263

b. Linear or spool valve selectors

Answer 264

c. Electrical locks

Answer 265

d. Non-return valves (NRV)

Answer 266

Fly by Light and is based on the use of optic fibre

Answer 267

Fod by Landing

Answer 268

Fresh Beacon Light and its use as a navaid is crucial

Answer 269

Fly by Light

Answer 270

Electronic Auto-Pilot, siendo el prototipo del F14

Answer 271

Experimental Aircraft Programme, siendo el prototipo de F22

Answer 272

Extreme Aerobatic Performance, siendo el prototipo del F35

Answer 273

Experimental Aircraft Programme, siendo el prototipo del EFA2000

Answer 274

Es un sistema muy utilizado y desarrollado

Answer 275

Evita las interferencias electromagnéticas

Answer 276

Es más estético

Answer 277

Evita el uso de superficies de vuelo

Answer 278

El uso de anticongelante líquido que se rociaba sobre el borde de ataque a través de unas perforaciones en el mismo

Answer 279

El uso de anticongelante líquido que se rociaba en vuelo desde la cabina mediante el uso de mangueras

Answer 280

El uso de energía eléctrica que impedía la formación de hielo

Answer 281

No existió tal sistema durante la década de los 40

Answer 282

Disminuye siempre

Answer 283

No afecta a la performance

Answer 284

El hielo no puede adherirse al ala en vuelo

Answer 285

No pueden prevenir la formación de hielo

Answer 286

Previenen la formación del hielo

Answer 287

Eliminan el hielo una vez formado

Answer 288

Son demasiado costosos para ser incluidos en vuelos comerciales

Answer 289

No pueden prevenir la formación de hielo

Answer 290

Previenen la formación del hielo

Answer 291

Eliminan el hielo una vez formado

Answer 292

Son demasiado costosos para ser incluidos en vuelos comerciales

Answer 293

Puede despegar con hielo formado porque existen sistemas a tal efecto

Answer 294

Nunca ha causado un accidente el despegar con hielo cargado

Answer 295

Siempre puede despegar con hielo, aunque no tenga un sistema anti hielo para eliminarlo posterior al despegue

Answer 296

Es responsable de que la aeronave despegue sin ninguna formación de hielo en la aeronave

Answer 297

b. Cylinder with silicon-based fluid

Answer 298

a. Are obsolete

Answer 299

b. Use oil and gas

Answer 300

c. Use a silicon-based fluid and gas

Answer 301

d. Only use a silicon-based fluid

Answer 302

a. Ensure that the wheel rotation plane is perpendicular to the surface

Answer 303

b. Provide prop ground clearance

Answer 304

c. Provide directional control in the ground

Answer 305

d. Avoid shimmy

Answer 306

a. Always can be rotated by the pilot from the cockpit

Answer 307

b. Can be directionally free

Answer 308

c. Can be locked with springs

Answer 309

d. Both b) and c) are correct

Answer 310

b. Banana with movable rod

Answer 311

c. Linear with movable rod

Answer 312

d. All the above are correct

Answer 313

a. 0,5 · Vstall

Answer 314

b. 1,3 · Vstall

Answer 315

c. 100 knots

Answer 316

d. 200 knots

Answer 317

a. Are used in the bogies of landing gears

Answer 318

b. Avoid pitching oscillations during braking the airplane

Answer 319

c. Both a) and b) and correct

Answer 320

d. All the above are incorrect

Answer 321

a. Creation of additional aerodynamic drag

Answer 322

b. Loss of cargo volume

Answer 323

c. Loss of fuel space

Answer 324

d. There are not disadvantages

Answer 325

a) They are expensive

Answer 326

b) They are toxic

Answer 327

c) They need a special seal

Answer 328

d) All are correct

Answer 329

a) The Martin Bridge

Answer 330

b) The Control Bridge

Answer 331

c) The Temperature Bridge

Answer 332

d) The Wheatstone Bridge

Answer 333

a) At high altitudes the air is more humid

Answer 334

b) At high altitudes the air is drier

Answer 335

c) It is not difficult, it is very easy

Answer 336

d) It is not possible to control the air humidity of that system

Answer 337

a) Between 10 and 12 m/min

Answer 338

b) Between 6 and 12 m/min

Answer 339

c) Between 5 and 10 m/min

Answer 340

d) Between 3 and 8 m/min

Answer 341

a) 15000 ft

Answer 342

b) 20000 ft

Answer 343

c) 25000 ft

Answer 344

d) 21000 ft

Answer 345

a) 7000 ft

Answer 346

b) 6000 ft

Answer 347

c) 10000 ft

Answer 348

d) 8000 ft

Answer 349

a) Pneumatic

Answer 350

b) Electro – pneumatic

Answer 351

c) Electronic

Answer 352

d) All are correct

Answer 353

a) Rapid decompression

Answer 354

b) Normal decompression

Answer 355

c) Explosive decompression

Answer 356

d) Slow decompression

Answer 357

Thermomether

Answer 358

All of the above

Answer 359

None of the above

Answer 360

Single-engine range

Answer 361

Vertical speed indicator

Answer 362

Turn indicator

Answer 363

Decreases air temperature

Answer 364

Increases air temperature

Answer 365

Can increase or decrease air temperature

Answer 366

Does not affect air temperature

Answer 367

Mercury thermometer

Answer 368

Thermistors

Answer 369

Thermocouples

Answer 370

Optical pyrometers

Answer 371

60 min ETOPS

Answer 372

120 min ETOPS

Answer 373

180 min ETOPS

Answer 374

370 min ETOPS

Answer 375

6 grouping

Answer 376

T grouping

Answer 377

It uses difgial displays

Answer 378

None of the above

Answer 379

a) Affect military aircraft cockpit through windscreen and canopy

Answer 380

b) Is a problem in fighters due to the large transparent cockpit to give good all around vision and the high altitude levels for fliying

Answer 381

c) When is combined with kinetic heating and rubber immersion or g-suits, special cooling measurements must be taken

Answer 382

d) All above are correct

Answer 383

a) Fliying to other countries (for example from a fairly warm area to a tropical area)

Answer 384

b) Fliying local flights

Answer 385

c) Fliying inside of Spain

Answer 386

d) Fliying upside down

Answer 387

a) In low altitudes it is needed cooling

Answer 388

b) In cruise altitudes it is needed heating due to the low temperatures

Answer 389

c) Both are true

Answer 390

d) Both are false

Answer 391

a) Need cooling

Answer 392

b) Need heating

Answer 393

c) Both are true depending on the season

Answer 394

d) Both are false

Answer 395

a) Air cycle machines

Answer 396

b) Vapor cycle machines

Answer 397

c) The fridge machine

Answer 398

d) A and B are correct

Answer 399

a) Hot air

Answer 400

b) Electrical heater

Answer 401

c) Combustion heater

Answer 402

d) All above are correct

Answer 403

a) CAU is the acronym of Cold Air Unit

Answer 404

b) CAU is the acronym of Cool Aircraft Unique

Answer 405

c) CAU is the acronym of Cold And Uncontrolled

Answer 406

d) All above are false

Answer 407

Eurofighter

Answer 408

Super Puma

Answer 409

Use electric pulses

Answer 410

Need hydraulic fluid to move control surfaces

Answer 411

Pilot must generate all the force to move the control surfaces

Answer 412

All are correct

Answer 413

Automatically activated when pilots fall asleep

Answer 414

Execute the control surface movement

Answer 415

It cannot be used on commercial planes

Answer 416

Guide the pilot how many degrees must change the attitude

Answer 417

They can be reversible or irreversible

Answer 418

Cables must be tensed to avoid free-play effects

Answer 419

They can only be used in small planes

Answer 420

None of the above

Answer 421

Commercial airplanes

Answer 422

Helicopters

Answer 423

a. Each fuel system is able to supply at least 100% of the fuel flow required

Answer 424

b. Fuel delivered at the same pressure every time

Answer 425

c. Must be fitted with a main pump + backup or emergency pump

Answer 426

d. a and c are true

Answer 427

a. Fuselage

Answer 428

c. Vertical Stabilizer

Answer 429

d. a and b are true

Answer 430

Rigid tanks

Answer 431

Flexible tanks

Answer 432

Integral tanks

Answer 433

None of the above

Answer 434

Prevent the overflow while fuelling

Answer 435

Allow expansion due to temperature changes

Answer 436

Prevent negative differential pressure

Answer 437

Avoid that the fuel vapors possible ignition propagate into the fuel tank

Answer 438

Prevent aeration

Answer 439

Avoid cavitation

Answer 440

Electrically driven

Answer 441

All of the above

Answer 442

Float, Zener Diode, Capacitance, Ultrasonic, Optical

Answer 443

Float, Zener Diode, Capacitance, Ultrasonic

Answer 444

Float, Led Diode, Capacitance, Ultrasonic, Optical

Answer 445

Float, Capacitance, Ultrasonic, Optical

Answer 446

Fuel On Booster

Answer 447

Fuel On Board

Answer 448

Fuel On Body

Answer 449

None of the above

Answer 450

Move fuel from the main wing and fuselage tanks to the collector tanks

Answer 451

Supply fuel to the engines

Answer 452

Assist in forcing the fuel under relatively low pressure from certain tanks to other more strategically placed

Answer 453

If an emergency or malfunction after TO happens, it throws a large portion of the fuel to reduce weight rapidly

Answer 454

A) Systems that allow the pilot to act on surfaces in different ways.

Answer 455

B) Include a system that the pilot will activate in an emergency.

Answer 456

C) Redundancy cannot be applied to hydraulic systems.

Answer 457

D) Doubling surface controls or acting elements.

Answer 458

A) Give a rapid response

Answer 459

B) Support reasonably light aerodynamic loads

Answer 460

C) Both A and B are correct

Answer 461

D) Support large aerodynamic loads

Answer 462

A) The power is infinite

Answer 463

B) Better results are obtained than with the other methods

Answer 464

C) It is not feasible to apply electrical power to the control of flight surfaces.

Answer 465

D) It does not require the presence of a high pressure hydraulic fluid.

Answer 466

A) If it is very high, the pilot will be more precise in the movements of the aircraft.

Answer 467

B) The stick force gradient will maintain the position established by the pilot when he releases the controls.

Answer 468

C) It can be proportional to air dynamic pressure, to flight control displacement or both of the previous.

Answer 469

D) This may be regulated by the pilot according to his preferences.

Answer 470

A) It is defined as techniques to reduce or cancel the force that is needed to act on control surfaces and obtain certain flight condition.

Answer 471

B) Can be produced with or without tabs.

Answer 472

C) It results useful at high speed and/or large control surface, when manual operation is difficult.

Answer 473

D) All of them are correct

Answer 474

A) You can have a direct or indirect control over the tab

Answer 475

B) The tabs always work autonomously, without the pilot being able to do any kind of action on them.

Answer 476

C) Tabs can only be implemented on ailerons.

Answer 477

D) These types of systems are not used in current aviation.

Answer 478

A) Its main function is to automatically trim the aircraft.

Answer 479

B) It's an indirect tab

Answer 480

C) They increase the necessary force to be applied by the pilot, increasing control.

Answer 481

D) Both B and C are correct

Answer 482

A) At high speeds they allow direct control over the Tab

Answer 483

B) At low speeds the spring constant decreases the necessary force

Answer 484

C) Both A and B are correct

Answer 485

D) The spring reduces the necessary force on all kinds of actions

Answer 486

A. There is no classification, every aircraft employs its own mechanism.

Answer 487

B. Type A, B, C and D.

Answer 488

C. Type 1, 2, 3 and 4.

Answer 489

D. Type A, B y C, but only applied to aircraft’s main gear.

Answer 490

A. Rotator or planing link mechanism.

Answer 491

B. Type A2.

Answer 492

C. Type B.

Answer 493

D. None of the above.

Answer 494

A. Increase of weight.

Answer 495

B. Increase of complexity

Answer 496

C. Increase of maintenance.

Answer 497

D. All the above.

Answer 498

A. A flashing yellow light for the whole gear.

Answer 499

B. A green light for every mechanism: nose gear/s and main gear/s.

Answer 500

C. A check from the Tower prior to landing.

Answer 501

D. When the red light inside the landing gear control lever stops flashing and remains on.

Answer 502

A. Heat energy.

Answer 503

B. Electric energy.

Answer 504

C. Magnetic energy.

Answer 505

D. Electromagnetic energy.

Answer 506

A. Electric power.

Answer 507

B. A steel cable connected to the cockpit.

Answer 508

C. Hydraulic systems.

Answer 509

D. The own aircraft’s weigh once it touches down.

Answer 510

A. Rotor and stator discs.

Answer 511

B. Several discs with their own braking pads.

Answer 512

C. Discs on each side of the wheel.

Answer 513

D. None of the above (A,B & C)

Answer 514

A. When the wheel suffers a puncture.

Answer 515

B. Only when landing in snowy conditions.

Answer 516

C. When the windshear is above 20 knots.

Answer 517

D. When a wheel is locked though the braking.

Answer 518

Single main

Answer 519

Taildragger

Answer 520

Double wheel

Answer 521

a) Withstand side loads when landing and taxiing

Answer 522

b) Absorb landing loads and damp vibrations

Answer 523

c) Possess a high drag coefficient

Answer 524

d) A and B are correct

Answer 525

The pilot has poor visibility when landing due to the elevation of the nose

Answer 526

The plane tends to turn over

Answer 527

The nose wheel generates a positive moment (forward)

Answer 528

All answers above are correct

Answer 529

It will be considered the two closest from the symmetry plane

Answer 530

It will be considered the two further from the symmetry plane

Answer 531

It will be considered the average of the outer distance

Answer 532

It will be considered the average of the inner distance

Answer 533

It is behind the main gear

Answer 534

It is in front of the main gear

Answer 535

It is indifferent

Answer 536

It depends on the plane

Answer 537

Fighter aircraft

Answer 538

Cargo airplanes

Answer 539

Passenger airplanes

Answer 540

That configuration does not exist

Answer 541

All answers above are correct

Answer 542

b) Vertical velocity at touch down

Answer 543

c) Horizontal velocity at touch down

Answer 544

d) All above are correct

Answer 545

Law 5/2005

Answer 546

The tires and wheels.

Answer 547

The windows of the cabin

Answer 548

The pitot tube

Answer 549

The control mobile surfaces, and their union with the fixed surfaces.

Answer 550

Compressor air

Answer 551

Pitot tube and static socket

Answer 552

Vacuum pump

Answer 553

Of the leading edge.

Answer 554

Compressor air

Answer 555

Pitot tube and static socket

Answer 556

Vacuum pump

Answer 557

Of the leading edge.

Answer 558

It is economical and weighs little

Answer 559

It is aerodynamic

Answer 560

It can be optimized by changing its shape

Answer 561

It is resistant to the king

Answer 562

Takeoff and landing

Answer 563

Every 15 minutes, in flight

Answer 564

It is not very aerodynamic and is incompatible with slats

Answer 565

It is very expensive

Answer 566

It is very heavy

Answer 567

It is not effective

Answer 568

Pneumatic boots

Answer 569

thermal antifreeze system

Answer 570

Electro-expulsion anti-icing system

Answer 571

Burning paste system

	Erstellt von 72 promocion vor mehr als 4 Jahre

Nächster

Avionica UD1&2

Beschreibung

Zusammenfassung der Ressource

Frage 1

Frage 2

Frage 3

Frage 4

Frage 5

Frage 6

Frage 7

Frage 8

Frage 9

Frage 10

Frage 11

Frage 12

Frage 13

Frage 14

Frage 15

Frage 16

Frage 17

Frage 18

Frage 19

Frage 20

Frage 21

Frage 22

Frage 23

Frage 24

Frage 25

Frage 26

Frage 27

Frage 28

Frage 29

Frage 30

Frage 31

Frage 32

Frage 33

Frage 34

Frage 35

Frage 36

Frage 37

Frage 38

Frage 39

Frage 40

Frage 41

Frage 42

Frage 43

Frage 44

Frage 45

Frage 46

Frage 47

Frage 48

Frage 49

Frage 50

Frage 51

Frage 52

Frage 53

Frage 54

Frage 55

Frage 56

Frage 57

Frage 58

Frage 59

Frage 60

Frage 61

Frage 62

Frage 63

Frage 64

Frage 65

Frage 66

Frage 67

Frage 68

Frage 69

Frage 70

Frage 71

Frage 72

Frage 73

Frage 74

Frage 75

Frage 76